CN114166478B - Method and device for measuring hysteresis rate of seal rigidization rate - Google Patents
Method and device for measuring hysteresis rate of seal rigidization rate Download PDFInfo
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- CN114166478B CN114166478B CN202111223581.1A CN202111223581A CN114166478B CN 114166478 B CN114166478 B CN 114166478B CN 202111223581 A CN202111223581 A CN 202111223581A CN 114166478 B CN114166478 B CN 114166478B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0075—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by means of external apparatus, e.g. test benches or portable test systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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Abstract
The invention discloses a seal rigidifying rate hysteresis rate measuring device, belongs to the technical field of engine seal component testing devices, and solves the technical problems of fingertip or brush seal rigidifying rate and hysteresis rate measurement. The device comprises a base and an end cover which is in sealing connection with the base, wherein a thrust device and a sealing runway which is arranged in an annular structure are installed in the base, the sealing runway is sleeved with a tested piece, a preset number of openings are formed in the circumferential preset position of the sealing runway, the openings are used for sealing the sealing runway in an airtight mode, when gas with preset pressure is filled in a sealing area formed by the base and the end cover, the sealing area is divided into a high-pressure side and a low-pressure side by the tested piece and/or the sealing runway, different thrust forces of the sealing runway are acted through the thrust device, and the sealing runway or the tested piece and the base are subjected to relative displacement so as to finish the measurement of the sealing rigidifying rate and the hysteresis rate of the tested piece. The invention aims to measure rigidization rate and hysteresis rate at quasi-side.
Description
Technical Field
The invention belongs to the technical field of engine sealing part testing, and particularly relates to a sealing rigidifying rate hysteresis rate measuring method and device.
Background
The long life, low leakage rate fingertip seal, which has practical value, is beneficial for improving component performance and engine thrust of gas turbine engines. The most direct value of fingertip seals and brush seals is to replace the comb seal at the high pressure differential area of the engine. Compared with the comb seal, the fingertip seal can reduce the air leakage of the engine by 1% -2%, and the fingertip seal is only used at the outlet part of the high-pressure compressor of the engine, so that the fuel consumption (SFC) of the engine is reduced by 0.7% -1.4%, and the direct use cost (DOC) is reduced by 0.3% -0.7%. Tests prove that the novel flexible seal such as fingertip seal, brush seal and the like has lower leakage rate than the comb seal and lower power loss than the comb seal and the circumferential graphite seal.
The service condition, service life and sealing performance of the fingertip seal are directly related to the contact rigidity of the fingertip sheet and the seal runway in the working process. The larger the contact rigidity is, the larger the heat productivity of the seal is, the abrasion is increased when the temperature exceeds the friction allowable temperature, and the service life of the fingertip seal is shortened. At the same time, the working conditions of high temperature, high speed and high sealing pressure difference will affect the highest temperature of the working surface. Therefore, the design work of the contact type fingertip seal is always focused on how to keep the contact rigidity of the fingertip sheet and the seal runway at a proper value in the working process, so as to ensure the sealing performance, and improve the service condition and the service life of the fingertip seal. However, the current research on the fingertip seal contact stiffness mainly depends on simulation, and the effectiveness of a simulation result also lacks experimental evaluation.
Due to the influence of the sealing structure, friction force, working environment and the like, the conventional fingertip seal shows a hysteresis characteristic in sealing performance, namely, sealing pressure difference is unchanged, and when the rotating speed of the sealing rotor starts to enter a descending region from the highest point, the leakage flow coefficient of the fingertip seal does not return to the original position along a curve when the rotating speed rises, but rises to a relatively high position. With the increase of the external pressure, the friction force is obviously increased, the finger body is prevented from moving freely in the radial direction, and the radial rigidity of the finger body is increased, which is the rigidifying effect of the fingertip seal.
The "stiffening effect" and "hysteresis effect" of the fingertip seal can seriously affect the sealing performance of the fingertip seal. At present, the stiffening effect and the hysteresis effect are improved mainly by means of structural improvement, and the stiffening rate and the hysteresis rate of the fingertip seal and the brush seal are evaluated and measured by a method which is not effective for forming a system.
In view of this, the present invention has been made.
Disclosure of Invention
The invention aims to provide a seal rigidifying rate hysteresis rate measuring device which solves the technical problem of how to measure rigidifying rate and hysteresis rate of fingertip seal, brush seal and the like. The technical scheme of the scheme has a plurality of technical advantages, and the following description is provided:
the utility model provides a sealed rigidifying rate hysteresis ratio measuring device is applicable to the measurement of the sealed rigidifying rate and the hysteresis ratio of measured piece, include the base and with base sealing connection's end cover, install thrust unit and the sealed runway that the annular structure set up in the base, the measured piece cover is established sealed runway, and be in sealed runway circumference is preset the position and is set up the opening or the incision of preset quantity, wherein:
when the gas with preset pressure is filled into the sealing area formed by the base and the end cover, the measured piece and/or the sealing runway divide the sealing area into a high pressure side and a low pressure side, different thrusts are acted on the sealing runway through the thrusting device, and the sealing runway or the relative displacement generated by the measured piece and the base is used for completing the measurement of the sealing rigidifying rate and the hysteresis rate of the measured piece.
Secondly, a measuring method is provided, which is suitable for measuring the seal rigidization rate and hysteresis rate of the measured piece, and the method comprises the following steps:
s801, a sealing runway is arranged in a sealing area, the sealing runway is sleeved by the tested piece, and the outer surface of the tested piece abuts against the sealing area; friction pieces made of flexible materials are filled in the circumferential part areas of the sealing runways; an opening or a gap is formed in a preset position of the sealing runway, and when high-pressure gas is supplemented, the measured piece and/or the sealing runway divide the sealing area into a high-pressure side and a low-pressure side;
s802, when the sealing runway is not sleeved by the tested piece, acquiring a first force F of the sealing runway pushed by a thrust device to a specified or preset displacement yc And, the preset position is moved back to the second force F pushing to the initial position hc ；
S803, when the closed area is in a zero pressure environment and the sealing runway is sleeved by the tested piece, obtaining a third force F of the sealing runway, which is pushed by a thrust device to a specified or preset displacement y0 And, preset position is moved back to the fourth force F pushing to the initial position h0 ；
S804, obtaining when the pressure difference between the high pressure side and the low pressure side is a preset value in a preset high pressure environmentTaking the fifth force F of the sealing runway pushed by the pushing device to a specified or preset displacement yi And, preset position is moved back to push to the sixth force F of the initial position hi ；
S805, determining the seal rigidifying rate and the hysteresis rate of the tested piece according to the force of the thrust device under different environments.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
the device of the scheme carries out unilateral promotion through thrust device, and when high pressure environment test, the air leakage of high pressure side can be reduced to the opening on the sealed runway, accomplishes the test through the displacement volume of sealed runway. The device can evaluate the rigidity performance of the sealing device, and the evaluation result has traction effect on the design, analysis and improvement of the fingertip seal and the brush seal, so that a test basis can be provided for the forward design of the fingertip seal and the brush seal.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained from them without inventive effort for a person skilled in the art.
FIG. 1 is a front cross-sectional view of the device of the present invention;
FIG. 2 is a schematic view of a sealing runway;
FIG. 3 is a schematic view of a sealing runway opening;
FIG. 4 is an assembly view of a test piece and a sealing runway;
1, a measured piece; 2. a base; 3. an end cap; 4. a thrust device; 5. a graphite ring; 6. sealing the runway; 7. an opening; 8. a leakage hole; 9. and a supporting seat.
Detailed Description
Other advantages and effects of the present invention will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present invention with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. The invention may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present invention. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present invention by way of illustration, and only the components related to the present invention are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details. In order to better understand the aspects of the present invention, the present invention will be described in further detail with reference to the accompanying drawings and detailed description. The terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The seal hardening rate hysteresis rate measuring device shown in fig. 1 is suitable for measuring the seal hardening rate and hysteresis rate of the measured object 1, and the measured object 1 is, for example, a fingertip seal, a brush seal, a circumferential graphite seal, an end-face graphite seal, or other sealing devices having the same function. The sealing rigidifying rate hysteresis rate measuring device comprises a base 2 and an end cover 3 which is in sealing connection with the base 2, wherein a thrust device 4 and a sealing runway 6 which is arranged in an annular structure are arranged in the base 2. The tested piece 1 is sleeved with the sealing runway 6, a preset number of openings 7 or notches are arranged at preset positions in the circumferential direction of the sealing runway 6, the openings 7 or notches are used for airtight sealing of the sealing runway 6 in a high-pressure environment, and the positions of the openings 7 or notches are symmetrically arranged on the sealing runway 6, for example.
When the sealed area formed by the base 2 and the end cover 3 is filled with gas with preset pressure, the sealed area is divided into a high pressure side and a low pressure side by the tested piece 1 and/or the sealing runway 6, at this time, when the sealing runway 6 is pushed to a specified displacement, the opening 7 or the notch can reduce gas leakage from the high pressure side to the low pressure side, a gas shielding surface is formed through a gap of the opening 7 or the notch, for example, under the action force of a single side of the thrust device 4, one side of the sealing runway 6 is stressed, the other side of the sealing runway 6 forms a gap with the tested piece 1, the opening 7 or the notch is arranged to prevent gas leakage, the high pressure side and the low pressure side meet the preset pressure difference, and the measurement of the tested piece under the preset pressure difference is ensured, so that the performance of the tested piece 1 under the real working environment of the engine is better simulated.
During testing, different thrusts, preferably, single-side thrusts, are applied to the sealing runway 6 through the thrust device 4, and when the sealing runway 6 or the tested piece 1 and the base 2 generate relative displacement, the measurement of the sealing rigidifying rate and the hysteresis rate of the tested piece 1 is completed.
As shown in fig. 4, in an assembly diagram of the sealing track 6 and the tested piece 1, a plurality of grooves are formed on the inner ring surface of the tested piece 1 in a brush sealing manner in the prior art.
As shown in fig. 2 and 3, the opening 7 is a folded line and/or an arc, the arc is S-shaped, the folded line is Z-shaped, or a combination of the two, so as to form a tight and narrow air-tight area, prevent air leakage from the high pressure side to the low pressure side, and reduce pressure leakage of the high pressure side and the low pressure side of the tested piece 1 in the closed area.
Further, the folded edge type is a Z-shaped row and is circumferentially arranged along the sealing runway 6, or an opening 7 formed by the arc-shaped structure and the folded edge type, or an opening 7 formed by the arc-shaped structure symmetrically.
The sealing rigidifying rate hysteresis rate measuring device is selected from products in the prior art, for example, the thrust device 4 comprises a telescopic rod, a pressure sensor and a displacement measuring device, wherein: the pressure sensor measures the force of the telescopic rod acting on the sealing track 6,
the displacement measuring device measures the displacement of the test piece 1 under the action of the opening 7 or the slit.
As a specific embodiment provided in the present case, the base 2 is disposed in an annular structure, and the outer surface of the measured member 1 abuts against the inner surface of the base 2.
Furthermore, a supporting table or a supporting seat 9 or a supporting frame, etc. are installed inside the base 2, and can bear the sealing runway 6, and the measured piece 1 can not be borne, and the measured piece 1 is resisted on the inner side wall of the base 2 by the sealing runway 6.
In the above device, grooves are formed on the opposite surfaces of the sealing track 6 and the base 2, and flexible friction members are embedded or filled in the grooves to reduce friction force, for example, the flexible friction members are square ring structures made of graphite materials to reduce friction force with the base 2, and are circular rings with rectangular cross sections.
Examples
The sealing runway 6 is provided with a Z-shaped opening 7, when the designated displacement of the sealing runway 6 is 0, the Z-shaped opening 7 is closed, and when the designated displacement of the sealing runway 6 is greater than 0, the Z-shaped opening 7 is opened. Fig. 3 is a schematic view of the opening of the "Z" shaped opening 7. The zigzag opening 7 is effective to reduce leakage of air from the high pressure chamber to the low pressure chamber when the sealing runway 6 is moving.
The sealing runway 6 is provided with the graphite ring 5, the graphite ring 5 is also provided with the Z-shaped opening 7 (graphite ring 5), and the Z-shaped opening 7 (graphite ring 5) on the graphite ring 5 is staggered with the Z-shaped opening 7 on the sealing runway 6 in the circumferential direction (refer to figure 4) during installation, so that air leakage is reduced. The graphite ring 5 is in interference fit with the sealing track 6. Sliding friction is reduced by the high roughness and flatness requirements of the mating surface of the graphite ring 5 and the measuring base 2. If necessary, the gas leakage can be measured through the gas leakage hole 8, and fine correction can be performed by the software of the prior art.
In another aspect, the present invention provides a method for measuring the seal rigidifying rate and hysteresis rate of a measured piece, where the method for measuring hysteresis rate includes, but is not limited to, using the following methods, and examples include:
s801, a sealing runway is arranged in a sealing area, a tested piece of the sealing runway is sleeved, and the outer surface of the tested piece abuts against the sealing area; friction pieces made of flexible materials are filled in the peripheral part area of the sealing runway; an opening or a gap is formed in a preset position of the sealing runway, and when high-pressure gas is fed in, the measured piece and/or the sealing runway divide the sealing area into a high-pressure side and a low-pressure side;
s802, when the sealing runway is not sleeved by the tested piece, acquiring a first force F of the sealing runway, which is pushed by the thrust device to a specified or preset displacement yc And, the preset position is moved back to the second force F pushing to the initial position hc ；
S803, when the closed area is in a zero-pressure environment and the sealed runway is sleeved by the tested piece, obtaining a third force F of the sealed runway, which is pushed by the thrust device to perform specified or preset displacement y0 And, preset position is moved back to the fourth force F pushing to the initial position h0 ；
S804, in the preset high-pressure environment, the pressure difference between the high-pressure side and the low-pressure side is presetWhen the value is set, a fifth force F of the sealing runway, which is pushed by the thrust device to a specified or preset displacement, is obtained yi And, preset position is moved back to push to the sixth force F of the initial position hi ；
S805, determining the seal rigidifying rate and the hysteresis rate of the tested piece according to the force of the thrust device under different environments.
Specifically, the method for determining the seal rigidifying rate and the hysteresis rate of the measured piece comprises the following steps:
determining the pressure Cheng Gangdu K of the tested sealing device according to the force of the thrust device under different environments yi Stiffness in return K hi And satisfies:
wherein D is a preset displacement;
hysteresis ratio sigma i Rate of rigidification delta i The following respectively satisfy:
，/>。
the specific implementation steps of the rigidity rate and hysteresis rate measurement of the tested sealing device are as follows:
step one: the rigidity and hysteresis rate measuring device is calibrated without installing the sealing device to be measured, the displacement giving device applies radial displacement D from 0.2mm to 1mm (interval of 0.2 mm) to the sealing runway, and the force Fyc required by the sealing runway to move to the specified displacement is measured by the force measuring device and recorded. The displacement of the sealing track was reduced from 1mm to 0.2mm by the displacement giving means, while the force Fhc required for the sealing track to move to the specified displacement was measured by the force measuring means and recorded.
Step two: at a differential pressure of 0, a sealing track is applied by a displacement giving device from 0.2mm to 1mm (spacing 0.1mm-0.2 mm)Radial displacement D while measuring the force F required by the sealing track to move to a specified displacement by the force measuring device y0 And recorded.
Step three: the displacement of the sealing track is reduced from 1mm to 0.2mm by the displacement giving means, while the force F required for the sealing track to move to the specified displacement is measured by the force measuring means h0 And recorded.
Step four: inputting high-pressure air into the measuring device, and sequentially completing the first step and the second step when the sealing pressure difference is 0.1MPa, 0.2MPa, 0.3MPa, 0.4MPa and 0.5MPa (the sealing pressure difference is the pressure of the high-pressure side pressure and the low-pressure side pressure), and recording the phase stress F measured by the force measuring device yi F (F) hi (i distinguishes the measurement results under different differential pressure conditions, i=0 represents a differential pressure of 0MPa, i=1 represents a differential pressure of 0.1MPa, and so on).
Step five: the pressure Cheng Gangdu Kyi, the return stiffness Khi, the hysteresis rate σi, and the rigidifying rate δi of the sealing device to be measured are calculated, and the calculation formula is shown in equations (1) - (4). The calculation results are recorded in a record table (refer to table 1).
··············（1）
·············（2）
············（3）
The following table is used for recording the contents (4),
the product provided by the invention is described in detail above. The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the core concepts of the invention. It should be noted that it will be apparent to those skilled in the art that several improvements and modifications can be made to the invention without departing from the inventive concept, and these improvements and modifications fall within the scope of the appended claims.
Claims (6)
1. The utility model provides a sealed rigidifying rate hysteresis ratio measuring device, is applicable to the measurement of the sealed rigidifying rate and the hysteresis ratio of measured piece, its characterized in that, include the base and with base sealing connection's end cover, install thrust unit and the sealed runway that the annular structure set up in the base, the measured piece cover is established sealed runway, and in the sealed runway circumference is preset the position and is set up opening or the incision of preset quantity, opening or incision are used for the gas tightness seal of sealed runway, wherein:
when the gas with preset pressure is filled into a sealing area formed by the base and the end cover, the sealed area is divided into a high-pressure side and a low-pressure side by the tested piece and/or the sealing runway, different thrusts are acted on the sealing runway through the thrusting device, and the sealing runway or the relative displacement generated by the tested piece and the base is used for completing the measurement of the sealing rigidifying rate and the hysteresis rate of the tested piece;
the thrust device comprises a telescopic rod, a pressure sensor and a displacement measuring device, wherein: the pressure sensor measures acting force of the telescopic rod on the sealing runway, and the displacement measuring device measures displacement generated by the measured piece under the action of the opening or the notch.
2. The seal stiffening rate hysteresis rate measurement device of claim 1, wherein the opening is hemmed and/or curved to reduce pressure leakage of the test piece on the high pressure side and the low pressure side within the enclosed area.
3. The seal hardening rate hysteresis rate measuring device according to claim 2, wherein the hemming type is provided in a zigzag shape along a circumference of the seal runway, or an opening formed by an arc structure and the hemming type, or an opening formed by an arc structure symmetrically.
4. The seal stiffening rate hysteresis rate measurement device of claim 1, wherein the outer surface of the part under test abuts the inner surface of the base.
5. The seal stiffening rate hysteresis rate measurement device of claim 1, wherein a groove is provided in the facing surface of the sealing runway and the base, and a flexible friction member is embedded or filled in the groove.
6. The seal stiffening rate hysteresis rate measurement device of claim 5, wherein the flexible friction member is a square ring structure made of graphite material to reduce friction with the base.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111223581.1A CN114166478B (en) | 2021-10-20 | 2021-10-20 | Method and device for measuring hysteresis rate of seal rigidization rate |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111223581.1A CN114166478B (en) | 2021-10-20 | 2021-10-20 | Method and device for measuring hysteresis rate of seal rigidization rate |
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| CN114166478B true CN114166478B (en) | 2023-09-05 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6196550B1 (en) * | 1999-02-11 | 2001-03-06 | Alliedsignal Inc. | Pressure balanced finger seal |
| US6364316B1 (en) * | 1999-02-11 | 2002-04-02 | Honeywell International Inc. | Dual pressure balanced noncontacting finger seal |
| CN101749055A (en) * | 2009-12-25 | 2010-06-23 | 中国燃气涡轮研究院 | Involute-type fingertip sealing structure |
| CN106567747A (en) * | 2016-10-08 | 2017-04-19 | 清华大学 | Low-hysteresis contact type fingertip seal with fin |
| CN107702868A (en) * | 2017-08-15 | 2018-02-16 | 沈阳航空航天大学 | A kind of brush seal experimental apparatus for capability vdiverse in function |
| CN108005793A (en) * | 2017-12-27 | 2018-05-08 | 中国航发四川燃气涡轮研究院 | A kind of tile sealing structure |
| CN110195617A (en) * | 2019-07-19 | 2019-09-03 | 中国航发沈阳发动机研究所 | A kind of finger sealing device |
| CN113028059A (en) * | 2021-04-15 | 2021-06-25 | 中国航发湖南动力机械研究所 | Bearing cavity dynamic seal device and aircraft engine thereof |
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2021
- 2021-10-20 CN CN202111223581.1A patent/CN114166478B/en active Active
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| US6196550B1 (en) * | 1999-02-11 | 2001-03-06 | Alliedsignal Inc. | Pressure balanced finger seal |
| US6364316B1 (en) * | 1999-02-11 | 2002-04-02 | Honeywell International Inc. | Dual pressure balanced noncontacting finger seal |
| CN101749055A (en) * | 2009-12-25 | 2010-06-23 | 中国燃气涡轮研究院 | Involute-type fingertip sealing structure |
| CN106567747A (en) * | 2016-10-08 | 2017-04-19 | 清华大学 | Low-hysteresis contact type fingertip seal with fin |
| CN107702868A (en) * | 2017-08-15 | 2018-02-16 | 沈阳航空航天大学 | A kind of brush seal experimental apparatus for capability vdiverse in function |
| CN108005793A (en) * | 2017-12-27 | 2018-05-08 | 中国航发四川燃气涡轮研究院 | A kind of tile sealing structure |
| CN110195617A (en) * | 2019-07-19 | 2019-09-03 | 中国航发沈阳发动机研究所 | A kind of finger sealing device |
| CN113028059A (en) * | 2021-04-15 | 2021-06-25 | 中国航发湖南动力机械研究所 | Bearing cavity dynamic seal device and aircraft engine thereof |
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| Title |
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| 指尖密封迟滞特性的机理分析;苏华;陈国定;;机械工程学报(第05期);全文 * |
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| CN114166478A (en) | 2022-03-11 |
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